US3216699A - Airfoil member assembly - Google Patents

Airfoil member assembly Download PDF

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Publication number
US3216699A
US3216699A US318557A US31855763A US3216699A US 3216699 A US3216699 A US 3216699A US 318557 A US318557 A US 318557A US 31855763 A US31855763 A US 31855763A US 3216699 A US3216699 A US 3216699A
Authority
US
United States
Prior art keywords
grooves
blade
spacer
groove
members
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US318557A
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English (en)
Inventor
William E Schoenborn
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US318557A priority Critical patent/US3216699A/en
Priority to GB20791/64A priority patent/GB1022386A/en
Priority to DE19641426806 priority patent/DE1426806A1/de
Priority to FR978024A priority patent/FR1524972A/fr
Priority to BE654781D priority patent/BE654781A/xx
Application granted granted Critical
Publication of US3216699A publication Critical patent/US3216699A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the general object of the present invention is a means for assembling and dis-assembling individual turbomachinery airfoil members arranged in a row in a supporting structure and having contiguous abut- 3,216,699 Patented Nov. 9, 1965 ting vibration reducing or stiffening means projecting laterally of the airfoils intermediate the radial lengths thereof.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US318557A 1963-10-24 1963-10-24 Airfoil member assembly Expired - Lifetime US3216699A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US318557A US3216699A (en) 1963-10-24 1963-10-24 Airfoil member assembly
GB20791/64A GB1022386A (en) 1963-10-24 1964-05-20 Improvements in a rotor assembly for turbine and like bladed machines
DE19641426806 DE1426806A1 (de) 1963-10-24 1964-06-04 Fluegelkoerpergruppe
FR978024A FR1524972A (fr) 1963-10-24 1964-06-12 Dispositif d'assemblage, notamment d'organes aérodynamiques de turbomachines
BE654781D BE654781A (de) 1963-10-24 1964-10-23

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US318557A US3216699A (en) 1963-10-24 1963-10-24 Airfoil member assembly

Publications (1)

Publication Number Publication Date
US3216699A true US3216699A (en) 1965-11-09

Family

ID=23238676

Family Applications (1)

Application Number Title Priority Date Filing Date
US318557A Expired - Lifetime US3216699A (en) 1963-10-24 1963-10-24 Airfoil member assembly

Country Status (4)

Country Link
US (1) US3216699A (de)
BE (1) BE654781A (de)
DE (1) DE1426806A1 (de)
GB (1) GB1022386A (de)

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3378230A (en) * 1966-12-16 1968-04-16 Gen Electric Mounting of blades in turbomachine rotors
US3383095A (en) * 1967-09-12 1968-05-14 Gen Electric Lock for turbomachinery blades
US3477795A (en) * 1967-05-01 1969-11-11 Rolls Royce Bladed rotor for a fluid flow machine
US3508844A (en) * 1968-07-25 1970-04-28 United Aircraft Corp Blade lock
US3524712A (en) * 1966-05-17 1970-08-18 Rolls Royce Compressor blade for a gas turbine engine
US3653781A (en) * 1970-12-18 1972-04-04 Gen Electric Turbomachinery blade retainer
US3734646A (en) * 1972-02-02 1973-05-22 Gen Electric Blade fastening means
US3832092A (en) * 1973-10-19 1974-08-27 Gen Electric Device for locking turbomachinery blades
US4207029A (en) * 1978-06-12 1980-06-10 Avco Corporation Turbine rotor assembly of ceramic blades to metallic disc
US4221542A (en) * 1977-12-27 1980-09-09 General Electric Company Segmented blade retainer
US4798519A (en) * 1987-08-24 1989-01-17 United Technologies Corporation Compressor part span shroud
US5460488A (en) * 1994-06-14 1995-10-24 United Technologies Corporation Shrouded fan blade for a turbine engine
US5667361A (en) * 1995-09-14 1997-09-16 United Technologies Corporation Flutter resistant blades, vanes and arrays thereof for a turbomachine
US5695323A (en) * 1996-04-19 1997-12-09 Westinghouse Electric Corporation Aerodynamically optimized mid-span snubber for combustion turbine blade
JPH108907A (ja) * 1996-03-21 1998-01-13 Soc Natl Etud Constr Mot Aviat <Snecma> ブロワ羽根の根元を保持する装置
WO2000031378A1 (en) * 1998-11-23 2000-06-02 Pratt & Whitney Canada Corp. Turbine blade to disk retention device
US6837686B2 (en) 2002-09-27 2005-01-04 Pratt & Whitney Canada Corp. Blade retention scheme using a retention tab
GB2408296A (en) * 2003-11-22 2005-05-25 Rolls Royce Plc Compressor blade root retainer with integral sealing means to reduce axial leakage
US20050254951A1 (en) * 2002-06-27 2005-11-17 Anne Thenaisie Restraining device for fan blade root
US20090060746A1 (en) * 2007-08-30 2009-03-05 Honeywell International, Inc. Blade retaining clip
US20090220343A1 (en) * 2008-02-29 2009-09-03 General Electric Company Hub pitch gear repair method
US20110142650A1 (en) * 2009-12-14 2011-06-16 Beeck Alexander R Turbine Blade Damping Device with Controlled Loading
US20110142654A1 (en) * 2009-12-14 2011-06-16 Marra John J Turbine Blade Damping Device With Controlled Loading
US20120027605A1 (en) * 2010-07-27 2012-02-02 Snecma Propulsion Solide Turbomachine blade, a rotor, a low pressure turbine, and a turbomachine fitted with such a blade
US20130156591A1 (en) * 2011-12-16 2013-06-20 United Technologies Corporation Energy absorbent fan blade spacer
US20140169976A1 (en) * 2012-12-18 2014-06-19 United Technologies Corporation Rotor blade root spacer for arranging between a rotor disk and a root of a rotor blade
US20140301854A1 (en) * 2013-04-04 2014-10-09 MTU Aero Engines AG Securement system and method for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base
US20150037161A1 (en) * 2013-07-30 2015-02-05 MTU Aero Engines AG Method for mounting a gas turbine blade in an associated receiving recess of a rotor base body
US20150240650A1 (en) * 2014-02-21 2015-08-27 Rolls-Royce Plc Rotor for a turbo-machine and a related method
USRE45690E1 (en) 2009-12-14 2015-09-29 Siemens Energy, Inc. Turbine blade damping device with controlled loading
US20160186581A1 (en) * 2014-12-29 2016-06-30 Rolls-Royce North American Technologies, Inc. Turbine wheels with preloaded blade attachment
US10508556B2 (en) 2013-01-17 2019-12-17 United Technologies Corporation Rotor blade root spacer with grip element
US10557356B2 (en) * 2016-11-15 2020-02-11 General Electric Company Combined balance weight and anti-rotation key
FR3093532A1 (fr) * 2019-03-06 2020-09-11 Safran Aircraft Engines Dispositif de ventilation d’une roue de turbine de turbomachine et/ou de retenue axiale d’aubes d’une telle roue
DE102019210647A1 (de) * 2019-07-18 2021-01-21 Siemens Energy Global GmbH & Co. KG Schaufelkranz für eine axiale Turbomaschine
US12018590B1 (en) 2023-04-04 2024-06-25 Ge Infrastructure Technology Llc Method for turbine blade and assembly with dovetail arrangement for enlarged rotor groove

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1084537A (en) * 1965-07-31 1967-09-27 Rolls Royce A compressor or turbine rotor for a gas turbine engine
US4846628A (en) * 1988-12-23 1989-07-11 United Technologies Corporation Rotor assembly for a turbomachine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2421890A (en) * 1944-11-27 1947-06-10 Goetaverken Ab Turbine blade
DE834408C (de) * 1950-11-23 1952-03-20 Maschf Augsburg Nuernberg Ag Vorverspannte axiale Schaufelfussbefestigung fuer Dampf- und Gasturbinen
FR1095392A (fr) * 1953-12-01 1955-06-01 Csf Aubages de turbines à gaz
US2955799A (en) * 1957-02-11 1960-10-11 United Aircraft Corp Blade damping means

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2421890A (en) * 1944-11-27 1947-06-10 Goetaverken Ab Turbine blade
DE834408C (de) * 1950-11-23 1952-03-20 Maschf Augsburg Nuernberg Ag Vorverspannte axiale Schaufelfussbefestigung fuer Dampf- und Gasturbinen
FR1095392A (fr) * 1953-12-01 1955-06-01 Csf Aubages de turbines à gaz
US2955799A (en) * 1957-02-11 1960-10-11 United Aircraft Corp Blade damping means

Cited By (49)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3524712A (en) * 1966-05-17 1970-08-18 Rolls Royce Compressor blade for a gas turbine engine
US3378230A (en) * 1966-12-16 1968-04-16 Gen Electric Mounting of blades in turbomachine rotors
US3477795A (en) * 1967-05-01 1969-11-11 Rolls Royce Bladed rotor for a fluid flow machine
US3383095A (en) * 1967-09-12 1968-05-14 Gen Electric Lock for turbomachinery blades
US3508844A (en) * 1968-07-25 1970-04-28 United Aircraft Corp Blade lock
US3653781A (en) * 1970-12-18 1972-04-04 Gen Electric Turbomachinery blade retainer
US3734646A (en) * 1972-02-02 1973-05-22 Gen Electric Blade fastening means
US3832092A (en) * 1973-10-19 1974-08-27 Gen Electric Device for locking turbomachinery blades
US4221542A (en) * 1977-12-27 1980-09-09 General Electric Company Segmented blade retainer
US4207029A (en) * 1978-06-12 1980-06-10 Avco Corporation Turbine rotor assembly of ceramic blades to metallic disc
US4798519A (en) * 1987-08-24 1989-01-17 United Technologies Corporation Compressor part span shroud
US5460488A (en) * 1994-06-14 1995-10-24 United Technologies Corporation Shrouded fan blade for a turbine engine
US5667361A (en) * 1995-09-14 1997-09-16 United Technologies Corporation Flutter resistant blades, vanes and arrays thereof for a turbomachine
JPH108907A (ja) * 1996-03-21 1998-01-13 Soc Natl Etud Constr Mot Aviat <Snecma> ブロワ羽根の根元を保持する装置
US5820347A (en) * 1996-03-21 1998-10-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Restraining device for the root of a fan blade
US5695323A (en) * 1996-04-19 1997-12-09 Westinghouse Electric Corporation Aerodynamically optimized mid-span snubber for combustion turbine blade
WO2000031378A1 (en) * 1998-11-23 2000-06-02 Pratt & Whitney Canada Corp. Turbine blade to disk retention device
US6109877A (en) * 1998-11-23 2000-08-29 Pratt & Whitney Canada Corp. Turbine blade-to-disk retention device
CZ298544B6 (cs) * 1998-11-23 2007-10-31 Pratt & Whitney Canada Corp. Upevnovací zarízení turbínové lopatky a zpusob sestavení
US20050254951A1 (en) * 2002-06-27 2005-11-17 Anne Thenaisie Restraining device for fan blade root
US7108484B2 (en) * 2002-06-27 2006-09-19 Snecma Moteurs Restraining device for fan blade root
US6837686B2 (en) 2002-09-27 2005-01-04 Pratt & Whitney Canada Corp. Blade retention scheme using a retention tab
GB2408296A (en) * 2003-11-22 2005-05-25 Rolls Royce Plc Compressor blade root retainer with integral sealing means to reduce axial leakage
US20090060746A1 (en) * 2007-08-30 2009-03-05 Honeywell International, Inc. Blade retaining clip
US20090220343A1 (en) * 2008-02-29 2009-09-03 General Electric Company Hub pitch gear repair method
US8287238B2 (en) * 2008-02-29 2012-10-16 General Electric Company Hub pitch gear repair method
US20110142654A1 (en) * 2009-12-14 2011-06-16 Marra John J Turbine Blade Damping Device With Controlled Loading
USRE45690E1 (en) 2009-12-14 2015-09-29 Siemens Energy, Inc. Turbine blade damping device with controlled loading
US8540488B2 (en) 2009-12-14 2013-09-24 Siemens Energy, Inc. Turbine blade damping device with controlled loading
US8616848B2 (en) 2009-12-14 2013-12-31 Siemens Energy, Inc. Turbine blade damping device with controlled loading
US20110142650A1 (en) * 2009-12-14 2011-06-16 Beeck Alexander R Turbine Blade Damping Device with Controlled Loading
US8951017B2 (en) * 2010-07-27 2015-02-10 Snecma Turbomachine blade, a rotor, a low pressure turbine, and a turbomachine fitted with such a blade
US20120027605A1 (en) * 2010-07-27 2012-02-02 Snecma Propulsion Solide Turbomachine blade, a rotor, a low pressure turbine, and a turbomachine fitted with such a blade
US20130156591A1 (en) * 2011-12-16 2013-06-20 United Technologies Corporation Energy absorbent fan blade spacer
US8851854B2 (en) * 2011-12-16 2014-10-07 United Technologies Corporation Energy absorbent fan blade spacer
US20140169976A1 (en) * 2012-12-18 2014-06-19 United Technologies Corporation Rotor blade root spacer for arranging between a rotor disk and a root of a rotor blade
US9422819B2 (en) * 2012-12-18 2016-08-23 United Technologies Corporation Rotor blade root spacer for arranging between a rotor disk and a root of a rotor blade
US10508556B2 (en) 2013-01-17 2019-12-17 United Technologies Corporation Rotor blade root spacer with grip element
US20140301854A1 (en) * 2013-04-04 2014-10-09 MTU Aero Engines AG Securement system and method for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base
US9677403B2 (en) * 2013-04-04 2017-06-13 MTU Aero Engines AG Securement system and method for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base
US20150037161A1 (en) * 2013-07-30 2015-02-05 MTU Aero Engines AG Method for mounting a gas turbine blade in an associated receiving recess of a rotor base body
US20150240650A1 (en) * 2014-02-21 2015-08-27 Rolls-Royce Plc Rotor for a turbo-machine and a related method
US10145247B2 (en) * 2014-02-21 2018-12-04 Rolls-Royce Plc Rotor for a turbo-machine and a related method
US10215035B2 (en) * 2014-12-29 2019-02-26 Rolls-Royce North American Technologies Inc. Turbine wheels with preloaded blade attachment
US20160186581A1 (en) * 2014-12-29 2016-06-30 Rolls-Royce North American Technologies, Inc. Turbine wheels with preloaded blade attachment
US10557356B2 (en) * 2016-11-15 2020-02-11 General Electric Company Combined balance weight and anti-rotation key
FR3093532A1 (fr) * 2019-03-06 2020-09-11 Safran Aircraft Engines Dispositif de ventilation d’une roue de turbine de turbomachine et/ou de retenue axiale d’aubes d’une telle roue
DE102019210647A1 (de) * 2019-07-18 2021-01-21 Siemens Energy Global GmbH & Co. KG Schaufelkranz für eine axiale Turbomaschine
US12018590B1 (en) 2023-04-04 2024-06-25 Ge Infrastructure Technology Llc Method for turbine blade and assembly with dovetail arrangement for enlarged rotor groove

Also Published As

Publication number Publication date
GB1022386A (en) 1966-03-09
DE1426806A1 (de) 1969-04-10
BE654781A (de) 1965-02-15

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